液体冲压发动机仿真模型研究  

A Simulation Model of Liquid Fuel Ramjet Engine

作　　者：张宏 陈玉春[1] 蔡元虎[1] 杨达[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《计算机仿真》2008年第7期70-72,共3页Computer Simulation

摘　　要：发展了一种弹用液体冲压发动机仿真模型。利用小偏离线性化理论和分段集总参数法,分别研究了超声速进气道、燃烧室和可调收敛喷管的建模方法。以正激波作为上边界,燃油流量的小变化作为扰动方程,喷管作为下边界,从而建立了液体冲压发动机仿真模型。根据所建立的仿真模型,对冲压发动机系统进行了仿真实验。仿真结果验证了仿真模型的有效性和合理性。该模型可用于液体冲压发动机控制系统的研究。A simulation model of liquid fuel ramjet engine for missile was developed.Modeling approach of supersonic inlet,combustor and variable convergent nozzle were studied respectively by using the small deviation linear theory and piecewise-lumped parameter method.The movable normal shock was used as the upstream boundary condition,the change in fuel flow rate of the combustor was treated as the disturbance equation,and variable convergent nozzle was assumed to be the downstream boundary condition,so the simulation model of liquid fuel ramjet engine was presented.According to the simulation model,ramjet engine system was simulated.Simulation results validate the rationality and validity of simulation model.This model can be applied to the control system research of liquid fuel ramjet engine for missile.

关 键 词：液体冲压发动机 仿真模型 扰动方程 边界条件 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]